[Federal Register Volume 80, Number 134 (Tuesday, July 14, 2015)]
[Rules and Regulations]
[Pages 40899-40903]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-15852]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0339; Directorate Identifier 2014-NM-025-AD; 
Amendment 39-18192; AD 2015-13-05]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 
series airplanes. This AD was prompted by reports of fatigue cracks 
found in the upper corners of the forward entry door skin cutout. This 
AD requires repetitive inspections for cracking in the upper corners of 
the forward entry door skin cutout, and repair if necessary. 
Accomplishment of this repair or a preventive modification terminates 
the repetitive inspections. We are issuing this AD to detect and 
correct cracking in the doorway upper corners, which could result in 
cabin depressurization.

DATES: This AD is effective August 18, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of August 18, 
2015.

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may view this referenced service information 
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., 
Renton, WA. For information on the availability of this material at the 
FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0339.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0339; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and 
other information. The address for the Docket Office (phone: 800-647-
5527) is Docket Management Facility, U.S. Department of Transportation, 
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 
New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Nenita Odesa, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; telephone: 
562-627-5234; fax: 562-627-5210; email: [email protected].

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to certain The Boeing Company 
Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. The 
NPRM published in the Federal Register on June 11, 2014 (79 FR 33484). 
The NPRM was prompted by reports of fatigue cracks found in the upper 
corners of the forward entry door skin cutout. The NPRM proposed to 
require repetitive inspections for cracking in the upper corners of the 
forward entry door skin cutout, and repair if necessary. Accomplishment 
of this repair or a preventive modification would terminate the 
repetitive inspections. We are issuing this AD to detect and correct 
cracking in the doorway upper corners, which could result in cabin 
depressurization.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM (79 
FR 33484, June 11, 2014) and the FAA's response to each comment.

Support for the NPRM (79 FR 33484, June 11, 2014)

    Boeing stated that it supports the NPRM (79 FR 33484, June 11, 
2014).

Request To Clarify Terminating Action

    Southwest Airlines (SWA) requested confirmation that paragraph 
3.B.4. of the Accomplishment Instructions of Boeing Alert Service 
Bulletin 737-53A1163, Revision 1, dated January 8, 2014, is an 
acceptable terminating action for the inspection requirements of 
paragraph (g)(1) of this NPRM (79 FR 33484, June 11, 2014) for the 
repaired door corners.
    SWA stated that the repairs provided in Part 3 of the 
Accomplishment

[[Page 40900]]

Instructions of Boeing Service Bulletin 737-53-1163, dated December 21, 
1993, and in Part 3 of the Accomplishment Instructions of Boeing Alert 
Service Bulletin 737-53A1163, Revision 1, dated January 8, 2014, 
contain instructions using the service information figures or using the 
structural repair manual. SWA stated that there are no provisions in 
the NPRM (79 FR 33484, June 11, 2014) for repairs installed using FAA 
Form 8100-9 prior to the issuance of the NPRM. SWA stated that 
paragraph 3.B.4. of the Accomplishment Instructions of Boeing Alert 
Service Bulletin 737-53A1163, Revision 1, dated January 8, 2014, states 
that, ``For door corners that have a repair provided by Boeing and 
approved via FAA Form 8100-9 installed, the inspection in this service 
bulletin is not required for the repaired door corner(s).''
    We agree that paragraph 3.B.4. of the Accomplishment Instructions 
of Boeing Alert Service Bulletin 737-53A1163, Revision 1, dated January 
8, 2014, is an acceptable terminating action for the inspection 
requirements of paragraph (g)(1) of this AD. We have added a new 
paragraph (h)(3) to this AD accordingly.

Request To Change the Compliance Time

    SWA requested that the compliance time for paragraph (i) in the 
proposed AD (79 FR 33484, June 11, 2014) be revised. SWA suggested that 
the proposed requirement of paragraph (i) of the proposed AD state that 
the compliance time in table 3 of paragraph 1.E., ``Compliance'' of 
Boeing Alert Service Bulletin 737-53A1163, Revision 1, dated January 8, 
2014, be implemented during the operator's repair assessment program 
(RAP), provided that the operator's RAP was developed using the ``D6-
38669, Repair Assessment Guidelines-Model 737-100 to -500,'' and 
approved by the FAA principal maintenance inspector.
    SWA stated that the 60,000-total-flight-cycle requirement may not 
coincide with the operator's implementation of the ``D6-38669, Repair 
Assessment Guidelines-Model 737-100 to -500.'' SWA stated that 
airplanes with existing preventive modifications and repairs that have 
already surpassed the compliance time in table 3 of 1.E., 
``Compliance'' of Boeing Alert Service Bulletin 737-53A1163, Revision 
1, dated January 8, 2014, will immediately be rendered out of 
compliance by paragraph (i) of the proposed AD (79 FR 33484, June 11, 
2014) if the table 3 requirement of 1.E., ``Compliance'' of Boeing 
Alert Service Bulletin 737-53A1163, Revision 1, dated January 8, 2014, 
does not coincide with the operator's RAP.
    We partially agree with the commenter's request. We disagree with 
the commenter's proposed compliance time because our examination of 
this issue shows that the compliance period for the RAP may be too long 
to address the unsafe condition. However, we agree that some airplanes 
would be rendered immediately out of compliance, and therefore, a 
compliance grace period should be added. We have added a grace period 
of ``4,500 flight cycles after the effective date of this AD'' to the 
compliance time in paragraph (i) of this AD.

Request To Provide Conditional Relief From Inspection Requirements

    SWA requested that the NPRM (79 FR 33484, June 11, 2014) provide 
relief from the external detailed inspection in areas that are hidden 
by an existing non-corner Boeing repair approved using FAA form 8100-9. 
SWA stated that an external detailed inspection is still required in 
the area not hidden by the repair.
    We agree with the commenter's request. As we stated previously, we 
have added a new paragraph (h)(3) to this AD for door corners that have 
an existing repair installed, as provided by Boeing and approved using 
FAA Form 8100-9. Under these conditions, the inspection in paragraph 
(g)(1) of this AD is not required for the repaired door corners.

Request to Revise the Requirements for Post-Modification and Post-
Repair Inspections

    SWA requested that the post-modification and post-repair 
inspections specified in table 3 of paragraph 1.E., ``Compliance,'' of 
Boeing Alert Service Bulletin 737-53A1163, Revision 1, dated January 8, 
2014, not be required in paragraph (i) of the proposed AD (79 FR 33484, 
June 11, 2014). SWA stated that the post-modification and post-repair 
inspections are currently mandated under 14 CFR 129.109(b)(2)14 and CFR 
121.1109(c)(2).
    We partially agree with the commenter's request. As we stated 
previously, our examination of this issue shows that the compliance 
period for the RAP may be too long to address the unsafe condition. 
However, we agree that these inspections are required under 14 CFR 
129.109(b)(2)14 and CFR 121.1109(c)(2). Operators who have already 
begun inspections of this area using the RAP should not be burdened 
with an additional and identical inspection requirement. Therefore, we 
have redesignated paragraph (i) of the proposed AD (79 FR 33484, June 
11, 2014) as paragraph (i)(1) and added new paragraph (i)(2) to this 
final rule, which states that the inspection requirement in paragraph 
(i)(1) of this AD does not apply to operators who have added 
inspections of this area in accordance with 14 CFR 121.1109(c)(2) or 
Sec.  129.109(b)(2) to their FAA-approved maintenance program. These 
inspections may be used in support of compliance with 14 CFR 
121.1109(c)(2) or Sec.  129.109(b)(2).

Effect of Winglets on AD

    Aviation Partners Boeing stated that accomplishing the supplemental 
type certificate (STC) ST01219SE does not affect the actions specified 
in the NPRM (79 FR 33484, June 11, 2014).
    We concur with the commenter. We have redesignated paragraph (c) of 
the NPRM (79 FR 33484, June 11, 2014) as (c)(1) and added new paragraph 
(c)(2) to this final rule to state that installation of STC ST01219SE 
(http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/
ebd1cec7b301293e86257cb30045557a/$FILE/ST01219SE.pdf http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/ebd1cec7b301293e86257cb30045557a/%24FILE/ST01219SE.pdf)) does not 
affect the ability to accomplish the actions required by this final 
rule. Therefore, for airplanes on which STC ST01219SE is installed, a 
``change in product'' alternative method of compliance (AMOC) approval 
request is not necessary to comply with the requirements of 14 CFR 
39.17.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the change described previously, and minor editorial 
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (79 FR 33484, June 11, 2014) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (79 FR 33484, June 11, 2014).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin 737-53A1163, dated 
December

[[Page 40901]]

21, 1993; and Boeing Alert Service Bulletin 737-53A1163, Revision 1, 
dated January 8, 2014. The service information describes repetitive 
inspections for cracking in the upper corners of the forward entry door 
skin cutout, and repair if necessary. Accomplishment of this repair or 
a preventive modification terminates the repetitive inspections. This 
service information is reasonably available because the interested 
parties have access to it through their normal course of business or by 
the means identified in the ADDRESSES section of this AD.

Costs of Compliance

    We estimate that this AD affects 371 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                        Estimated Costs--Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                        Cost per    Cost on U.S.
                Action                            Labor cost             Parts cost      product      operators
----------------------------------------------------------------------------------------------------------------
Inspection............................  3 work-hours x $85 per hour =            $0          $255       $94,605
                                         $255.
----------------------------------------------------------------------------------------------------------------


                                        Estimated Costs--Optional Actions
----------------------------------------------------------------------------------------------------------------
                                                                                                          Cost on
             Action                     Labor cost            Parts cost           Cost per product         U.S.
                                                                                                         operators
------------------------------------------------------------------------------------------------------- -----------
Preventive modification........  44 work-hours x $85 per  Up to $3,912......  Up to $7,652.
                                  hour = $3,740.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary repairs that 
would be required based on the results of the inspection. We have no 
way of determining the number of aircraft that might need these 
repairs:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                          Cost on
             Action                     Labor cost            Parts cost           Cost per product         U.S.
                                                                                                         operators
------------------------------------------------------------------------------------------------------- -----------
Repair.........................  60 work-hours x $85 per  Up to $4,964......  Up to $10,064.
                                  hour = $5,100.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
a cost estimate for the post-repair or post-preventive modification 
inspections specified in this AD.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII: Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    This AD will not have federalism implications under Executive Order 
13132. This AD will not have a substantial direct effect on the States, 
on the relationship between the national government and the States, or 
on the distribution of power and responsibilities among the various 
levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2015-13-05 The Boeing Company: Amendment 39-18192; Docket No. FAA-
2014-0339; Directorate Identifier 2014-NM-025-AD.

(a) Effective Date

    This AD is effective August 18, 2015.

(b) Affected ADs

    None.

(c) Applicability

    (1) This AD applies to The Boeing Company Model 737-100, -200, -
200C, -300, -400, and -500 series airplanes; certificated in any 
category; as identified in Boeing Alert Service Bulletin 737-
53A1163, Revision 1, dated January 8, 2014.
    (2) Installation of Supplemental Type Certificate (STC) 
ST01219SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/
rgstc.nsf/0/ebd1cec7b301293e86257cb30045557a/$FILE/ST01219SE.pdf 
http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/ebd1cec7b301293e86257cb30045557a/%24FILE/ST01219SE.pdf) does not 
affect the

[[Page 40902]]

ability to accomplish the actions required by this AD. Therefore, 
for airplanes on which STC ST01219SE is installed, a ``change in 
product'' alternative method of compliance (AMOC) approval request 
is not necessary to comply with the requirements of 14 CFR 39.17.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

    This AD was prompted by reports of fatigue cracks found in the 
upper corners of the forward entry door skin cutout. We are issuing 
this AD to detect and correct cracking in the doorway upper corners, 
which could result in cabin depressurization.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Inspection

    (1) For airplanes identified in Boeing Alert Service Bulletin 
737-53A1163, Revision 1, dated January 8, 2014, as Groups 1 and 2, 
Configuration 2, and Group 3: Before the accumulation of 27,000 
total flight cycles, or within 4,500 flight cycles after the 
effective date of this AD, whichever occurs later, do an external 
detailed inspection for cracking of the skin assembly, and a low 
frequency eddy current (LFEC) inspection for cracking of the skin 
assembly and bear strap, and all applicable corrective actions, in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 737-53A1163, Revision 1, dated January 8, 2014, 
except as required by paragraph (j) of this AD. Repeat the 
inspections thereafter at intervals not to exceed 4,500 flight 
cycles. Do all applicable corrective actions before further flight.
    (2) For airplanes identified as Group 4 in Boeing Alert Service 
Bulletin 737-53A1163, Revision 1, dated January 8, 2014: Within 120 
days after the effective date of this AD, do inspections of the skin 
assembly and bear strap and all applicable corrective actions using 
a method approved in accordance with the procedures specified in 
paragraph (m) of this AD.

(h) Terminating Actions

    (1) Accomplishment of the preventive change specified in Part II 
of the Accomplishment Instructions of Boeing Service Bulletin 737-
53-1163, dated December 21, 1993; or the preventive modification 
specified in Part 2 of the Accomplishment Instructions of Boeing 
Alert Service Bulletin 737-53A1163, Revision 1, dated January 8, 
2014; terminates the inspection requirements specified in paragraph 
(g)(1) of this AD.
    (2) Accomplishment of the repair specified in Part III of the 
Accomplishment Instructions of Boeing Service Bulletin 737-53-1163, 
dated December 21, 1993; or Part 3 of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 737-53A1163, Revision 
1, dated January 8, 2014; terminates the inspection requirements 
specified in paragraph (g)(1) of this AD.
    (3) For door corners that have a repair installed, as provided 
by Boeing, which inhibits the inspections required by paragraph 
(g)(1) of this AD, and approved before the effective date of this AD 
using FAA Form 8100-9, the inspection in paragraph (g)(1) of this AD 
is not required. Refer to the repair approval for any supplemental 
inspection of the repair area.

(i) Post-Modification and Post-Repair Inspections

    (1) For airplanes identified in Boeing Alert Service Bulletin 
737-53A1163, Revision 1, dated January 8, 2014, as Groups 1 and 2, 
on which a repair or preventive modification has been installed in 
accordance with Boeing Service Bulletin 737-53-1163, dated December 
21, 1993; or Boeing Alert Service Bulletin 737-53A1163, Revision 1, 
dated January 8, 2014: At the applicable time specified in table 3 
of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
737-53A1163, Revision 1, dated January 8, 2014, or within 4,500 
flight cycles after the effective date of this AD, whichever occurs 
later, inspect the fuselage skin assembly, bear strap, and frame and 
sill outer chords, as applicable, for cracking, in accordance with 
table 3 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 737-53A1163, Revision 1, dated January 8, 2014. Repeat the 
inspection thereafter at the times specified in table 3 of paragraph 
1.E., ``Compliance'' of Boeing Alert Service Bulletin 737-53A1163, 
Revision 1, dated January 8, 2014. If any crack is found during any 
inspection required by this paragraph, repair before further flight 
using a method approved in accordance with the procedures specified 
in paragraph (m) of this AD.
    (2) The inspection requirement in paragraph (i)(1) of this AD 
does not apply to operators who have added the inspection program 
for this area specified in table 3 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1163, 
Revision 1, dated January 8, 2014, in accordance with 14 CFR 
121.1109(c)(2) or Sec.  129.109(b)(2) to their FAA-approved 
maintenance program. These inspections may be used in support of 
compliance with 14 CFR 121.1109(c)(2) or Sec.  129.109(b)(2).

(j) Exception to Service Information Specifications

    If any cracking is found during any inspection required by this 
AD, and Boeing Alert Service Bulletin 737-53A1163, Revision 1, dated 
January 8, 2014, specifies to contact Boeing for appropriate action: 
Before further flight, repair the crack using a method approved in 
accordance with the procedures specified in paragraph (m) of this 
AD.

(k) Explanation of Service Information and AD: Repair/Preventative 
Modification Required

    The Accomplishment Instructions of Boeing Alert Service Bulletin 
737-53A1163, Revision 1, dated January 8, 2014, state that Group 1 
and 2, Configuration 1 airplanes on which the repair or preventive 
modification has been installed as specified in Boeing Service 
Bulletin 737-53-1163, dated December 21, 1993, are not required to 
be inspected. However, this AD requires inspections of Group 1 and 2 
airplanes, as identified in and in accordance with paragraph (i) of 
this AD, which correspond with table 3 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1163, 
Revision 1, dated January 8, 2014.

(l) Credit for Previous Actions

    This paragraph provides credit for the actions specified in 
paragraph (g) of this AD, if those actions were performed before the 
effective date of this AD using Boeing Service Bulletin 737-53-1163, 
dated December 21, 1993.

(m) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles Aircraft Certification Office 
(ACO), FAA, has the authority to approve AMOCs for this AD, if 
requested using the procedures found in 14 CFR 39.19. In accordance 
with 14 CFR 39.19, send your request to your principal inspector or 
local Flight Standards District Office, as appropriate. If sending 
information directly to the manager of the ACO, send it to the 
attention of the person identified in paragraph (n)(1) of this AD. 
Information may be emailed to: [email protected].
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD if it is approved by the 
Boeing Commercial Airplanes Organization Designation Authorization 
(ODA) that has been authorized by the Manager, Los Angeles ACO, to 
make those findings. For a repair method to be approved, the repair 
must meet the certification basis of the airplane and the approval 
must specifically refer to this AD.

(n) Related Information

    (1) For more information about this AD, contact Nenita Odesa, 
Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles ACO, 
3960 Paramount Boulevard, Lakewood, CA 90712-4137; telephone: 562-
627-5234; fax: 562-627-5210; email: [email protected].
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (o)(3) and (o)(4) of this AD.

(o) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Boeing Service Bulletin 737-53-1163, dated December 21, 
1993.
    (ii) Boeing Alert Service Bulletin 737-53A1163, Revision 1, 
dated January 8, 2014.
    (3) For Boeing service information identified in this AD, 
contact Boeing Commercial Airplanes, Attention: Data &

[[Page 40903]]

Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-
2207; telephone 206-544-5000, extension 1; fax 206-766-5680; 
Internet https://www.myboeingfleet.com.
    (4) You may view this referenced service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, 
call 425-227-1221.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on June 19, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-15852 Filed 7-13-15; 8:45 am]
 BILLING CODE 4910-13-P